Interchangeable internal modular avionics platform assembly

ABSTRACT

Internal interchangeable modular avionics platform assemblies and methods for removably mounting and interchanging modular avionics platforms within an aircraft. In some embodiments, modular avionics platform assemblies may include a modular avionics platform configured to support various avionics equipment, suitable for removable mounting within a forward fuselage, and interchangeable with a number of alternate platforms. A platform may include a frame structure, and mounting pins and a connector assembly disposed on the frame structure. The mounting pins may project outwardly from the frame structure to align with and detachably secure to corresponding airframe members of an aircraft when the frame structure is in a mounted position. The connector assembly may be disposed on the frame structure and have a plurality of connectors, including connectors for alternating current, direct current, and data. In some embodiments, the platform may also include an environmental cooling system disposed on the frame structure.

FIELD

This disclosure relates to interchangeable modular avionics platformassemblies and methods for removably mounting and interchanging modularavionics platforms within an aircraft. More specifically, the disclosedembodiments relate to modular avionics platforms configured to supportvarious avionics equipment, suitable for removable mounting within aforward fuselage of an aircraft, and interchangeable with a number ofalternate modular avionics platforms.

BACKGROUND

For various reasons, it may be desirable to modularly install selectedavionics equipment onto an aircraft. Conventional solutions for modularinstallation of avionics equipment include removably mounting anequipment “pod” to an exterior of the aircraft. Various equipment podsmay be specialized to perform a variety of equipment-dependent missions,e.g., reconnaissance, electronic jamming, etc., and include sets ofavionics equipment pertaining to those missions. For example, anequipment pod suitable for reconnaissance missions may include variouscameras and sensors, and may be temporarily mounted on a lower exteriorportion of the aircraft. Although the equipment pod may be suitable formeeting mission objectives, external mounting of the equipment pods maybe problematic and thus undesirable.

For example, an externally mounted equipment pod may add unwanted bulkto the aircraft, which may adversely affect performance of the aircraft,such as by reducing cruise speed. Accordingly, flight testing may berequired to measure any adverse effects the equipment pod may have onaircraft performance. Additionally, external mounting of the equipmentpods may be an inefficient use of storage space on the aircraft, such asby occupying external stores of the aircraft instead of utilizingexisting internal stores of the aircraft. Moreover, the equipment podsmay have limited modularity, i.e., be difficult to customize, in thataddition and/or removal of avionics equipment from the pod may bedifficult. In other words, the equipment pods may not be fullycustomizable to meet the needs of any equipment-dependent mission.

A custom reconnaissance assembly having imaging devices for use duringreconnaissance missions also exists that replaces a gun assembly in aforward gun bay of certain aircraft. This assembly uses mountingassemblies including fixed or pivot pins with slotted plates or clampassemblies to secure it to the aircraft airframe. This assembly is notavailable for different types of aircraft and is limited to the singleuse of reconnaissance.

SUMMARY

The present disclosure relates to interchangeable modular avionicsplatform assemblies and methods for removably mounting and interchangingmodular avionics platforms within a forward fuselage of an aircraft. Insome embodiments, the disclosed assemblies may include a modularavionics platform suitable for removable mounting within the forwardfuselage and interchangeable with a number of alternate modular avionicsplatforms, wherein each platform includes a frame structure, at leastone pair of mounting pins disposed on the frame structure, and aconnector assembly disposed on the frame structure. The frame structuremay have substantially parallel opposing side portions spaced apart at apredetermined width so that the frame structure fits between opposingairframe members within a forward interior bay of a fuselage of anaircraft with each side portion proximate a corresponding airframemember. Each of the at least one pair of mounting pins may be disposedon and axially aligned with a respective one of the opposing sideportions of the frame structure and configured to project outwardly fromeach respective opposing side portion to align with and detachablysecure to the corresponding airframe member when the frame structure isin a mounted position. The connector assembly may be disposed on theframe structure and have a plurality of connectors, including analternating current connector configured to connect to a 115-voltalternating current source, a direct current connector configured toconnect to a 28-volt direct current source, and a data bus connectorconfigured to connect to a data bus of the aircraft. Additionally, someembodiments may include an environmental cooling system disposed on theframe structure. The modular avionics platform may be mountable withinand non-destructively releasably removable from the forward interior bayof the fuselage as to be interchangeable with a number of alternatemodular avionics platforms, with each modular avionics platform beingconfigured to support one or more of avionics equipment having differentdimensions, and to thereby enable modular installation of selectedavionics equipment into the aircraft to perform a variety ofequipment-dependent missions.

In some embodiments, an aircraft may have a fuselage with a forwardinterior bay having laterally opposing airframe members and configuredfor removable mounting of a gun therein. An interchangeable modularavionics platform may be removably mounted to the airframe memberswithin the forward interior bay. The platform may include asubstantially rectangular frame structure having opposing side portionsproximate to the airframe members. The frame structure may include aplurality of outwardly projecting mounting pins disposed on and axiallyaligned with the side portions, including a first pair of mounting pinsand a second pair of mounting pins spaced apart from the first pair ofmounting pins. Each mounting pin may be positioned on the framestructure to align with and detachably secure to a corresponding clampassembly disposed on the airframe members. A plurality of clampassemblies may be disposed on the airframe members in positionscorresponding to positions of the mounting pins on the frame structure.The plurality of clamp assemblies may include a first pair of clampassemblies corresponding to the first pair of mounting pins and a secondpair of clamp assemblies corresponding to the second pair of mountingpins. Each clamp assembly may be configured to detachably secure acorresponding mounting pin and have a fixed clamp element fixedlyattached to a respective airframe member, and a pivot clamp elementconfigured to pivot between an open position in which the correspondingmounting pin is not clamped, and a closed position in which thecorresponding mounting pin is clamped into place relative to the clampassembly. The modular avionics platform may be configured to bemountable within and non-destructively releasably removable from theforward interior bay of the fuselage by the plurality of clampassemblies as to be interchangeable with a number of alternate modularavionics platforms. Each modular avionics platform may be configured tosupport one or more of avionics equipment having different dimensions,and to thereby enable modular installation of selected avionicsequipment into the aircraft to perform a variety of equipment-dependentmissions.

In some embodiments, a method may include removably mounting aninterchangeable modular avionics platform within a forward interior bayof an aircraft, including attaching a plurality of clamp assemblies toopposing airframe members within the forward interior bay, disposing aplurality of mounting pins onto the platform to align with correspondingclamp assemblies, and detachably securing the mounting pins to thecorresponding clamp assemblies.

Features, functions, and advantages may be achieved independently invarious embodiments of the present disclosure, or may be combined in yetother embodiments, further details of which can be seen with referenceto the following description and drawings.

BRIEF DESCRIPTION OF THE DRAWINGS

FIG. 1 is a perspective view of a front portion of an aircraft showing aforward interior bay in a fuselage of the aircraft, with aninterchangeable modular avionics platform assembly disposed within theforward interior bay.

FIG. 2 is a top isometric view showing an interchangeable modularavionics platform including at least one pair of mounting pins disposedon opposing side portions of the platform.

FIG. 3 is bottom isometric view showing the interchangeable modularavionics platform of FIG. 2.

FIG. 4 is top view showing the interchangeable modular avionics platformof FIGS. 2-3.

FIG. 5 is a partially transparent isometric view showing a cutawayportion of a forward interior bay of an aircraft, including a pluralityof slot and clamp assemblies attached to opposing airframe members ofthe forward interior bay.

FIG. 6 is an enlarged view of the clamp assembly of FIG. 5, including amounting pin secured within the clamp assembly.

FIG. 7 is a flowchart depicting a method for removably mounting andinterchanging an interchangeable modular avionics platform within aforward interior bay of an aircraft, and/or reconfiguring selectedavionics equipment disposed on the modular avionics platform.

DESCRIPTION Overview

Various embodiments of an interchangeable modular avionics platformassembly and related methods are described below and illustrated in theassociated drawings. Unless otherwise specified, the modular avionicsplatform assembly and/or its various components may, but are notrequired to, contain at least one of the structure, components,functionality, and/or variations described, illustrated, and/orincorporated herein. Furthermore, the structures, components,functionalities, and/or variations described, illustrated, and/orincorporated herein in connection with the present teachings may, butare not required to, be included in other avionics platform assemblies.The following description of various embodiments is merely exemplary innature and is in no way intended to limit the disclosure, itsapplication, or uses. Additionally, the advantages provided by theembodiments, as described below, are illustrative in nature and not allembodiments provide the same advantages or the same degree ofadvantages.

General Features

This section describes general features of interchangeable internalmodular avionics platform assemblies; see FIG. 1.

FIG. 1 is a perspective view of a forward fuselage, generally indicatedat 10, of an aircraft 12. An interchangeable modular avionics platformassembly 14 is disposed within a forward interior bay 16 of aircraft 12.Although only forward fuselage 10 of aircraft 12 is shown in FIG. 1,some embodiments may include an entire aircraft 12. Alternativeembodiments may include only modular avionics platform assembly 14.

As shown in FIG. 1, forward interior bay 16 of forward fuselage 10 maybe located substantially between a nose 18 and a cockpit 20 of aircraft12, and may extend at least partially beneath cockpit 20. Forwardinterior bay 16 may be suitable for mounting of avionics equipmenttherein. For example, forward interior bay 16 may be a gun bay andsuitable for mounting of a gun therein. In such embodiments, removal ofthe gun may provide space for modular installation of other selectedavionics equipment. Specifically, modular avionics platform assembly 14may be disposed within forward interior bay 16 to thereby enable modularinstallation of various avionics equipment within aircraft 12.

More specifically, platform assembly 14 may include a modular avionicsplatform 22, which may be mountable within and non-destructivelyreleasably removable from interior bay 16 (i.e., non-destructivelyremovably mounted) as to be interchangeable with a number of alternatemodular avionics platforms. Additionally, each platform 22 may beconfigured to support one or more avionics equipment having differentdimensions, to thereby enable modular installation of selected avionicsequipment into aircraft 12 to perform a variety of equipment-dependentmissions. Selected avionics equipment may include but are not limited toany suitable custom and/or commercial off-the-shelf devices such ascameras, data link systems, track and sensor systems, radio terminals,environmental cooling systems, and/or other weapon replacementassemblies. For example, platform 22 may house one or more cameras andsupporting equipment for use in reconnaissance missions.

Regarding modularity of platform 22, any avionics equipment disposed onand/or within platform 22 may be interchangeable with any other suitableavionics equipment. More specifically, avionics equipment may be easilyadded to and/or removed from platform 22 so that one platform 22 may bea multipurpose platform 22, i.e., support different types of equipmentfor different types of equipment-dependent missions. Additionally oralternatively, multiple platforms 22 may be used, each platform beingconfigured for a specific equipment-dependent mission or set ofmissions. In other words, one platform 22 may be interchangeable withany number of alternate platforms 22 to perform a variety ofequipment-dependent missions.

Additionally, platform 22 may be configured to fit in any aircrafthaving a forward fuselage 10 that is or may be substantially hollow(e.g., have a gun bay from which the gun may be removed). As shown inFIG. 1, platform 22 may be substantially rectangular in shape andinclude opposite side portions 24 and 26 spaced apart at a width 25corresponding to a distance between corresponding opposing airframemembers 28 and 30 within forward interior bay 16 so that platform 22 mayfit between airframe members 28 and 30. Airframe members 28 and 30 mayprovide a mechanical structure for aircraft 12 and be substantiallyparallel to a longitudinal axis (not shown) defined by a length ofaircraft fuselage 10, as shown in FIG. 1. In some examples, airframemembers 28 and 30 may be transverse or even substantially perpendicularto the longitudinal axis of aircraft fuselage 10. Additionally, as shownin FIG. 1, platform 22 may be removably mounted to airframe members 28and 30.

As also shown in FIG. 1, embodiments of platform assembly 14 maygenerally include two mounting assemblies, shown generally at 32, formounting platform 22 to airframe members 28 and 30. Each mountingassembly 32 may include a first mounting device 34 disposed on a sideportion 24 or 26 to provide support for platform 22 by engagement with acomplementary second mounting device 36 disposed on the correspondingone of airframe members 28 and 30. In some embodiments, aircraft 12 maybe modified post-manufacture to include second mounting devices 36. Inother embodiments, aircraft 12 may have been manufactured to includesecond mounting devices 36. Any suitable number of mounting assemblies32 may be used.

Platform 22 may also include additional elements configured tocorrespond with certain components of aircraft 12. As shown in FIG. 1,such aircraft components may include one or more louvers 38, such as gungas vents, blast diffuser vents, etc., located on one or more sides offorward fuselage 10 and configured to vent exhaust from within forwardinterior bay 16 to an exterior of aircraft 12. Aircraft components mayalso include an access window 40, such as a gun mount upper access,located on an upper portion of forward fuselage 10. Access window 40 isdisposed to provide vertical support to a platform 22 by a hoist lineextending through the window to a hoist knob 42 disposed on platform 22.Additional aircraft components may include one or more access panels 44,such as an equipment access door, located on a bottom of forwardfuselage 10 and configured to enable insertion and/or removal of a gunassembly into and/or from forward interior bay 16. The locations oflouver(s) 38, access window 40, and access panel(s) 44 shown in FIG. 1are merely illustrative; different embodiments may or may not includethese components, and they may be located in alternative and/oradditional locations.

Modular avionics platform assemblies are discussed in more detail withrespect to Example 1 below; and methods for mounting, non-destructivelyremoving, and interchanging modular avionics platforms within aircraft12 are discussed in more detail with respect to Example 2 below.

EXAMPLES, COMPONENTS, AND ALTERNATIVES

The following sections describe selected aspects of an exemplaryinterchangeable modular avionics platform assembly as well as relatedmethods. The examples in these sections are intended for illustrationand should not be interpreted as limiting the entire scope of thepresent disclosure. Each section may include one or more distinctinventions, and/or contextual or related information, function, and/orstructure.

Interchangeable Internal Modular Avionics Platform Assemblies

This section describes specific features of interchangeable internalmodular avionics platform assemblies; see FIGS. 2-6.

Example 1

FIG. 2 is a top isometric view showing an interchangeable modularavionics platform 200, including at least one pair of mounting devices202 disposed on opposing side portions 204 and 206 of a frame structure208. Platform 200 is an example of a platform 22 described above.

As shown in FIG. 2, side portions 204 and 206 may be substantiallyparallel and spaced apart at a predetermined width W so that framestructure 208 fits between opposing airframe members 28 and 30 withinforward interior bay 16 of fuselage 10 of an aircraft 12, with each sideportion 204 and 206 proximate a corresponding airframe member 28 or 30.In other words, frame structure 208 may be configured to have anysuitable dimensions so that the frame structure may fit between opposingairframe members 28 and 30 of a forward interior bay 16 of any aircraft12. In some embodiments, frame structure 208 may be substantiallyrectangular in shape. However, more generally, frame structures 208 mayhave any suitable shape, such as but not limited to rectangular,trapezoidal, hexagonal, cylindrical, etc. Additionally, frame structure208 may consist of a material or mixture of materials suitable for usein aircraft 12, such as but not limited to metal, composite, epoxy,carbon fiber, wood, etc.

Side portions 204 and 206 of frame structure 208 may include at leastone pair of mounting devices 202, more specifically mounting pins 210.Each mounting pin 210 may be disposed on and axially aligned with arespective one of opposing side portions 204 and 206 of frame structure208, and configured to project outwardly from each respective sideportion 204 and 206 to align with and detachably secure to thecorresponding airframe member 28 or 30 when frame structure 208 is in amounted position. For example, as shown in FIG. 1, embodiments mayinclude two pairs of mounting pins 210 disposed on frame structure 208,including a first pair of mounting pins 210 spaced apart from a secondpair of mounting pins 210. In addition to being configured fordetachable securement to airframe members 28 and 30, mounting pins 210may be configured to provide support for platform 200 on airframemembers 28 and 30. Similar to frame structure 208, mounting pins 210 mayconsist of any material or mixture of materials suitable for use inaircraft 12.

Further, mounting pins 210 may be fixedly attached to frame structure208 in any suitable way. For example, as shown in FIG. 1, in someembodiments, mounting pins 210 may include a mounting plate 211 having aplurality of small apertures 214 configured to enable insertion ofbolts, screws, pins, etc. to thereby fasten mounting pins 210 to framestructure 208. Additionally or alternatively, mounting pins 210 may beglued, welded, etc.

to frame structure 208. In other embodiments, mounting pins 210 may be aseamless component of frame structure 208, e.g., where frame structure208 is additively manufactured. In general, each mounting pin 210 may bestationary, i.e., have a fixed position relative to frame structure 208.However, in some embodiments, mounting pins 210 may be nonstationary,i.e., have more than one position relative to frame structure 208. Forsimplicity, stationary pins are described as mounting pins, andnonstationary pins are described as pivot pins.

Some embodiments may include a pair of pivot pins 212, as indicated byphantom lines in FIG. 2. Pivot pins 212 may be another example ofmounting devices 202 and provide additional support and/or securementfor platform 200 on airframe members 28 and 30. Specifically, each pivotpin 212 may be disposed on and axially aligned with a respective sideportion 204 or 206 of frame structure 208, spaced apart from mountingpin(s) 210 on each side portion 204 and 206, and positioned to alignwith a corresponding slot on a corresponding airframe member 28 or 30when frame structure 208 is in a mounted position. Additionally, eachpivot pin 212 may be configured to have a stowed position within arecessed area 213 of the respective side portion 204 or 206 of framestructure 208, and an extended position configured to extend into thecorresponding slot on the corresponding airframe member 28 or 30 tothereby detachably secure frame structure 208 to airframe members 28 and30. In some embodiments, the stowed position may be substantiallyparallel to or otherwise extend along an axis defined by a length ofside portion 204 or 206. Pivot pins 212 are shown in FIG. 2 in theirextended positions. Similar to frame structure 208 and mounting pins 210and pivot pins 212 may consist of any material or mixture of materialssuitable for use in aircraft 12. The mounting assemblies shown anddescribed herein may be made according to designs known in the art asused on the existing custom reconnaissance assembly.

Additionally, as shown in FIG. 2, some embodiments may include a hoistelement, such as a hoist ring or hoist knob 218 disposed on framestructure 208 of platform 200. Hoist knob 218 may generally be fixedlyattached to frame structure 208 and include a structure configured todetachably secure to an external hoisting device suitable for liftingand/or lowering platform 200 within forward interior bay 16 of aircraft12. For example, some embodiments may be configured to have an aperturethrough which a hook of the external hoisting device may be inserted;platform 200 may thus be positioned within forward interior bay 16 fromoutside of aircraft 12. Additionally, hoist knob 218 may be configuredto enable the insertion and/or removal of platform 200 into and/or fromforward interior bay 16, such as by raising and/or lowering platform 200through access panel 44 (shown in FIG. 1).

Further, as shown in FIG. 2, some embodiments may include a connectorassembly 220 disposed on frame structure 208 and having a plurality ofconnectors configured to connect equipment disposed on frame structure208 to equipment disposed elsewhere in aircraft 12. For example,connector assembly 220 may include a 115-volt alternating current (AC)connector 222 configured to connect to 115-volt AC current source, a28-volt direct current (DC) connector 224 configured to connect to a28-volt DC current source, and a data bus connector 226 configured toconnect to a data bus of aircraft 12. Connector assembly 208 may alsoinclude one or more additional connectors 228, as shown in FIG. 2. Theadditional connector(s) may connect any suitable equipment and performany suitable function(s). Phantom lines have been drawn in FIG. 2 toindicate connector wires of aircraft 12 that may be attached toconnector assembly 220. Additionally, although connector assembly 220 isdisposed in FIG. 4 on a front portion of frame structure 208, connectorassembly 220 may generally be disposed on any suitable portion of framestructure 208, such as but not limited to an equipment rack of framestructure 208.

Additionally, frame structure 208 may include at least one equipmentrack having a plurality of equipment stations and configured to supportand enable detachable securement of selected avionics equipment thereon.For example, as shown in FIG. 2, the at least one equipment rack mayinclude a first equipment rack 230, and a second equipment rack 232disposed below first equipment rack 230. Each equipment rack may be ashelf structure and include a substantially continuous floor or suitableconfiguration of floor members. However, as shown in FIG. 2, firstequipment rack 230 may include a plurality of small apertures 234configured to enable insertion of bolts, screws, pins, etc. to therebyfasten selected avionics equipment to first equipment rack 230.Additionally, first equipment rack 230 may include a plurality of largerapertures 236 configured to enable threading of wires, tubing, and/orother suitable equipment therethrough. Second equipment rack 232 may besubstantially similar to first equipment rack 230.

Further, in some embodiments, first equipment rack 230 may include afirst equipment station 238; and second equipment rack 232 may include asecond equipment station 240 disposed above second equipment rack 232,and a third equipment station 242 disposed below second equipment rack232. In some embodiments, third equipment station 242 may be asubstantially open frame having a floor. Additionally, second equipmentstation 240 may be a substantially closed compartment. However, eachequipment station may have any suitable configuration and/or positioningon frame structure 208. Additionally, although equipment stations areshown in FIG. 2 as partitioned areas of their respective equipmentrack(s), embodiments may include any number of partitioned and/ornon-partitioned equipment stations. For example, as shown in FIG. 2,first equipment rack 230 may include an additional fourth equipmentstation 244 on a side of partition 246 opposite first equipment station238. Additionally, any suitable number of selected avionics equipmenthaving any suitable dimensions may be disposed, either permanently orremovably, within each equipment station.

For example, some embodiments may include an environmental coolingsystem, generally indicated at 248, included on and/or within platform200 and configured to provide cooling air to an electronic device 250disposed within platform 200. Environmental cooling system 248 mayprovide platform 200 with an internal system for cooling avionicsequipment independent of an environmental cooling system of aircraft 12in which platform 200 is mounted, thereby eliminating reliance onaircraft 12 for cooling and rerouting of aircraft environmental coolingsystem ducting to platform 200.

Specifically, FIG. 2 shows electronic device 250 disposed within secondequipment station 232, and a compressor 252 and a cooling fan 254 ofenvironmental cooling system 248 mounted in third equipment station 242.In some embodiments, compressor 252 may be a commercially availablecompressor that may connect to a 115-volt AC current source.Additionally, as shown in FIG. 2, environmental cooling system 248 mayinclude a length of flexible cooling tubing 256 that is in fluidcommunication with cooling fan 254 and extends to second equipmentstation 240 to thereby supply cooling air to second equipment station240. Environmental cooling system 248 may also include a length offlexible exhaust tubing 258 configured to conduct the heated cooling airfor heat removal from second equipment station 232 to louvers 38 inforward interior bay 16 of fuselage 10 of aircraft 12 in which platform200 is removably mounted (aircraft 12 shown in FIG. 1).

Other suitable avionics equipment may include, for example, any customand/or commercial off-the-shelf devices such as cameras, data linksystems, track and sensor systems, radio terminals, and/or other weaponreplacement assemblies. Certain aspects of selected avionics equipmentare described in more detail below.

FIG. 3 is bottom isometric view showing modular avionics platform 200 ofFIG. 2, including phantom lines indicating areas of platform 200 whereselected avionics equipment may be disposed. For simplicity,corresponding elements in the embodiment of FIG. 2 have been labeledusing the same reference characters.

As shown in FIG. 3, some embodiments frame structure 208 may furtherinclude a fifth equipment station 260 and a sixth equipment station 262in which additional avionics equipment may be disposed. Each equipmentstation may house any suitable avionics equipment having any suitabledimensions, not limited to the dimensions indicated by the phantom linesin FIG. 3.

For example, in some embodiments, fourth equipment station 244 may housea data link system 264 configured to sense and receive data communicatedbetween aircraft communication nodes, to enable at least one airborneaircraft 12 to control firing of other airborne aircraft weaponry at adesignated target by communicating using data link system 264. In someembodiments, fifth equipment station 260 may house a camera system 268configured for use in reconnaissance missions. Additionally, in someembodiments, sixth equipment station 262 may house an infraredsearch-and-track sensor system 270 configured to enable tracking ofother airborne aircraft. Further, in some embodiments, first equipmentstation 238 may house an internet-protocol-based mesh-network radioterminal 272 configured to enable data communication between multipleairborne aircraft including aircraft 12 in which platform 200 isremovably mounted.

Additionally, these equipment may be housed in any suitable equipmentstation(s), and alternative embodiments may include alternate equipment.Equipment may be selected based on mission requirements. As discussedwith respect to Example 1 above, selected equipment may be detachablysecured to platform 200 and interchangeable with alternate equipment sothat platform 200 may be used to perform a variety ofequipment-dependent missions. Additionally or alternatively, selectedequipment may be more permanently secured to platform 200 so thatplatform 200 may be interchangeable with a number of alternateplatforms, each platform being configured to perform one or morespecific equipment-dependent mission. In either case, platform 200 maybe mountable within and non-destructively releasably removable fromforward interior bay 16 of aircraft 12 in which platform 200 is mounted,to thereby enable modular installation of selected avionics equipment inaircraft 12 to perform a variety of equipment-dependent missions.

FIG. 4 is top view showing the interchangeable modular avionics platformof FIGS. 2-3, including a clearer view of mounting pins 210 and pivotpins 212. For simplicity, corresponding elements in the embodiment ofFIGS. 2-3 have been labeled using the same reference characters.

Although two pairs of mounting pins 210 are shown in FIG. 4, alternativeembodiments may include any suitable number of mounting pins 210disposed on frame structure 208, such as one pair of mounting pins 210or more than two pairs of mounting pins 210. Additionally, as indicatedby phantom lines in FIG. 4, embodiments may or may not include pivotpins 212. Pivot pins 212 are shown in FIG. 4 in their extendedpositions. Pivot pins 212 in their stowed positions may not be visiblefrom the top view due to being stowed in recessed areas 213 (shown inFIGS. 2-3) of frame structure 208. Additionally, embodiments may ingeneral include any suitable number and/or combination of mounting pins210 and/or pivot pins 212. For example, some embodiments may include onepair of mounting pins 210 and one pair of pivot pins 212; otherembodiments may include one pair of mounting pins 210 and two pairs ofpivot pins 212; and yet other embodiments may include two pairs ofmounting pins 210 and two pairs of pivot pins 212.

Additionally, some embodiments may include one or more pivot pins 212configured to have substantially the same function as mounting pins 210,so long as the pivot pins are in their extended positions. Morespecifically, an extended pivot pin 212 may be configured to detachablysecure to a corresponding clamp assembly in substantially the same wayas a mounting pin 210. However as described further with reference toFIGS. 5 and 6, pivot pins 212 may generally be configured to detachablysecure to corresponding slots in airframe members 28 and 30 withininterior bay 16 of aircraft 12, whereas mounting pins 210 may generallybe configured to detachably secure to corresponding clamp assembliesattached to airframe members 28 and 30 within interior bay 16 ofaircraft 12. Clamp assemblies and slots are discussed in further detailbelow.

FIG. 5 is an isometric view showing a cutaway portion of a forwardinterior bay 16 of an aircraft 12, including a plurality of brackets 273having slots 274 and clamp assemblies 276, as examples of secondmounting devices 278 attached to opposing airframe members 28 and 30 offorward interior bay 16. Each second mounting device 278 may beconfigured to enable modular interchangeability of platform 200 with anumber of alternate modular avionics platforms. Brackets 273, shown inphantom lines, may be an alternative to a clamp assembly 276, asdescribed further below. For simplicity, corresponding elements in theembodiment of FIG. 1 have been labeled using the same referencecharacters. As shown in FIG. 5, embodiments may include a plurality ofsecond mounting devices 278 disposed on airframe members 28 and 30within forward interior bay 16. Second mounting devices 278 arecomplementary to and form mounting assemblies with mounting devices 202disposed on frame structure 208 of platform 200. Mounting devices 202are shown in FIGS. 2-4. As mentioned above, second mounting devices 278may be made according to designs known in the art as used on theexisting custom reconnaissance assembly.

Each clamp assembly 276 may be configured to be attached to an opposingairframe member 28 or 30 corresponding to each position of acorresponding mounting pin 210 disposed on frame structure 208 shown inFIGS. 2-4. Each mounting pin 210 may be configured to enable modularinterchangeability of platform 200 with a number of alternate modularavionics platforms. Positions of mounting pins 210 relative to clampassemblies 276 are indicated by phantom lines in FIG. 6. Each clampassembly 276 may include a fixed clamp element 282 configured to befixedly attached to opposing airframe member 28 or 30, and a pivot clampelement 284 configured to pivot between an open position in which pivotclamp element 284 is spaced apart from fixed clamp element 282, and aclosed position in which pivot clamp element 284 is proximate to andsecured relative to fixed clamp element 282 to thereby detachably securecorresponding mounting pin 210 to corresponding airframe member 28 or30.

Fixed clamp elements 282 may be attached to airframe members 28 and 30in any suitable way. For example, fixed clamp elements 282 may eachinclude a plurality of small apertures configured to enable insertion ofbolts, screws, pins, etc. to thereby fasten fixed clamp elements 282 toairframe members 28 and 30. Additionally or alternatively, fixed clampelements 282 may be glued, welded, etc. to airframe members 28 and 30.Pivot clamp element 284 may also be attached to fixed clamp element 282in any suitable way. For example, as shown in FIG. 5, each pivot clampelement 284 may be attached to fixed clamp element 282 using a hinge pin286. Additionally, hinge pin 286 may allow pivot clamp element 284 topivot between an open position, shown in phantom lines in FIG. 6, and aclosed position, shown in solid lines in FIG. 6, relative to fixed clampelement 282. Similar to mounting pins 210, hinge pins 286 may consist ofany material or mixture of materials suitable for use in aircraft 12,such as but not limited to metal, composite, epoxy, etc.

Although clamp assemblies 276 may generally be configured to detachablysecure mounting pins 210, clamp assemblies 276 may additionally oralternatively support pivot pins 212 (shown in FIGS. 2-4) so long aseach pivot pin 212 is in an extended position.

Alternatively, pivot pins 212 may detachably secure to brackets 273 bypivoting into slots 274 in airframe members 28 and 30 when platform 200is supported in position, such as by a hoist and/or due to additionalmounting devices 202 on frame structure 208 being detachably secured tocomplementary second mounting devices 278 on airframe members 28 and 30.For example, in embodiments wherein mounting pins 210 are detachablysecured to corresponding clamp assemblies 276 on airframe members 28 and30, pivot pins 212 may be detachably secured to brackets 273 on airframemembers 28 and 30 to provide additional support for platform 200 withinforward interior bay 16 of aircraft 12.

Each bracket 273 may be attached to a corresponding airframe member 28or 30 corresponding to a position of a corresponding pivot pin 212, andconfigured with slot 274 to detachably receive the corresponding pivotpin 212 in its extended position. Slot 274 may be any suitable shapeand/or depth to receive and support pivot pin 212 therewithin.

Brackets 273 may be attached to airframe members 28 and 30 in anysuitable way. For example, brackets 273 may each include a plurality ofsmall apertures configured to enable insertion of bolts, screws, pins,etc. to thereby fasten brackets 273 to airframe members 28 and 30.Additionally or alternatively, brackets 273 may be configured to beglued, welded, etc. to airframe members 28 and 30. Further, brackets 273may consist of any suitable material or mixture of materials, similar toclamp assemblies 276. However, some embodiments may not include anybrackets 273. Embodiments not including brackets 273 may be, forexample, embodiments wherein pivot pins 212 in their extended positionsmay be detachably secured using clamp assemblies 276. Mounting devices202 may not include pivot pins 212 and airframe members 28 and 30 mayinclude preexisting slots 274. Slots 274 may have a width correspondingto a length of pivot pins 212 so that pivot pins 212 may be pivoted intotheir extended positions within slots 274 to thereby be detachablysecured within slots 274.

FIG. 6 is an enlarged view showing in further detail clamp assembly 276of FIG. 5, including a mounting pin 210 shown in phantom lines. As shownin FIG. 6, in some embodiments, clamp assembly 276 may include pivotclamp element 284 attached to fixed clamp element 282 by hinge pin 286.Specifically, pivot clamp element 284 may include an aperture configuredto align with a corresponding aperture in fixed clamp element 282,wherein each aperture is configured to enable insertion of hinge pin 286therethrough to thereby enable pivotal attachment of pivot clamp element284 to fixed clamp element 282. Additionally, one or more ends of hingepin 286 may be capped to prevent hinge pin 286 from falling out ofeither aperture. Further, pivot clamp element 284 may pivot around hingepin 286 to an open position 292, as indicated by phantom lines in FIG.6. Additionally, pivot clamp element 284 may pivot around hinge pin 286to a closed position proximate to and secured relative to fixed clampelement 282 to clamp corresponding mounting pin 210 to correspondingairframe member 28 or 30. As shown in FIG. 6, clamp assembly 276 maydetachably secure mounting pin 210 when pivot clamp element 284 is inthe closed position.

Further, as shown in FIG. 6, clamp assembly 276 may include a lockingmechanism, generally indicated at 294, and configured to lock pivotclamp element 284 in place relative to clamp element 282 when pivotclamp element 284 is in the closed position. Locking mechanism 294 mayinclude a locking member 296 configured to pivot around a second hingepin 298 to an unlocked position 300, as indicated by phantom lines inFIG. 6, wherein locking member 296 does not lock pivot clamp element 284in place relative to clamp assembly 276. Additionally, locking member296 may be configured to pivot around second hinge pin 298 to a lockedposition, wherein locking member 296 may lock pivot clamp element 284 inthe closed position.

Specifically, in some embodiments, locking mechanism 294 may include aledge structure 302 disposed on locking member 296 and configured tolock pivot clamp element 284 in place relative to fixed clamp element282. As shown in FIG. 6, ledge structure 302 may be configured to sitbelow a portion of pivot clamp element 284 and provide upward supportfor pivot clamp element 284 when pivot clamp element 284 is in theclosed position and locking member 296 is in the locked position.Additionally, when pivot clamp element 284 is in the closed position andlocking member 296 is in the locked position, ledge structure 302 mayrest in a recess in pivot clamp element 284, thereby preventing pivotclamp element 284 from pivoting to the open position 292. Additionally,ledge structure 302 may be adjustable in position on locking member 296between a raised position in which pivot clamp element 284 is locked inthe closed position and a lowered position in which pivot locking member296 is pivotable away from pivot claim element 284 to unlocked position300.

In some embodiments, pivot locking member 296 may be a locking bolt onwhich ledge structure 302 is mounted. The position of ledge structure302 on the locking bolt may then be manipulated by adjusting theposition of a locknut 304 on the locking bolt. Adjustment of locknut 304may raise and/or lower ledge structure 302 relative to second hinge pin298 to thereby lock and/or unlock pivot clamp element 284. Accordingly,mounting pin 210 may be detachably secured relative to each clampassembly 276 when mounting pin 210 is aligned within an aperture formedby clamp elements 282 and 284 of clamp assembly 276. For example, asshown in FIG. 6, clamp elements 282 and 284 may each include asemicircle-shaped aperture configured to form a circular aperture inwhich mounting pin 210 may be detachably secured when pivot clampelement 284 is in the closed position. Apertures formed by clampelements 282 and 284 may have any shape and dimension suitable fordetachably securing mounting pins 210.

In alternative embodiments, clamp assemblies 276 may include a fixedclamp element 282 and a movable clamp element 284 that is adjustablesimilar to the jaws of a conventional vise. Clamp assemblies 276 mayconsist of any material or mixture of materials suitable for use inaircraft 12, such as but not limited to metal, composite, epoxy, etc.

Methods for Removably Mounting Interchangeable Internal AvionicsPlatforms

This section describes methods for removably mounting, interchanging,and/or reconfiguring internal avionics platforms; see FIG. 7.

Aspects of avionics platform assemblies may be utilized in the methodsteps described below. Where appropriate, reference may be made topreviously described components and systems that may be used in carryingout each step. These references are for illustration, and are notintended to limit the possible ways of carrying out any particular stepof the method. Although various steps are described below and depictedin FIG. 7, the steps need not necessarily all be performed, and in somecases may be performed in a different order than the order shown.

Example 2

FIG. 7 is a flowchart illustrating operations performed by anillustrative method and may not recite the complete process or all stepsof the method. FIG. 7 depicts multiple steps of a method, generallyindicated at 700. Specifically, method 700 may be a method for removablymounting an interchangeable modular avionics platform within a forwardinterior bay of an aircraft 12, interchanging the modular avionicsplatform with an alternate modular avionics platform, and/orreconfiguring the modular avionics platform. Embodiments of modularavionics platform assemblies are shown in FIGS. 2-6 and described indetail with respect to Example 1 above. For simplicity, correspondingelements in the embodiments of FIGS. 2-6 are described in Example 2using the same reference characters.

A step 702 of method 700 may include providing an interchangeablemodular avionics platform 200 configured to support selected avionicsequipment having different dimensions. Platform 200 may include a framestructure 208 having substantially parallel opposing side portions 204and 206 spaced apart at a predetermined width W so that frame structure208 fits between opposing airframe members 28 and 30 within a forwardinterior bay 16 of a forward fuselage 10 of an aircraft 12, with eachside portion 204 and 206 proximate a corresponding airframe member 28 or30. In some embodiments, frame structure 208 may be manufactured to fitwithin a particular aircraft 12 and/or model of aircraft 12. In someembodiments, frame structure 208 may be manufactured during step 702.

For example, a user may obtain measurements of forward interior bay 16and manufacture frame structure 208 to fit within forward interior bay16. In other embodiments, frame structure 208 may be pre-manufacturedand known to be suitable for aircraft 12 in which platform 200 isintended to be removably mounted. Additionally, in embodiments whereinframe structure 208 includes at least one equipment rack having aplurality of equipment stations, the equipment rack(s) and/or stationsmay be manufactured to fit a variety of selected avionics equipmentthereupon and/or therein. For example, a user may configure a firstequipment station 238 to have dimensions suitable for a camera. In thatexample, first equipment station 238 may be positioned on a lowerportion of platform 200 and not include a floor, so that the camera maypoint downward to image elements below aircraft 12. Additionally, insome embodiments, equipment station 238 may have an open and/orpartially open frame, solid and/or partially solid floor, etc.Additionally or alternatively, equipment rack(s) and stations may bepre-manufactured and have generic dimensions and/or configurations.

Some embodiments may include platform 200 having selected avionicequipment disposed on equipment rack(s) and configured to perform aspecific mission or set of missions. For example, the avionics equipmentmay be pre-disposed on an equipment rack 230 and/or disposed onequipment rack 230 during step 702. The avionics equipment may bepre-disposed, partially pre-disposed, and/or disposed on equipment rack230 during step 702. For example, platform 200 may be designated for usein reconnaissance missions and include pre-disposed avionics equipmentsuitable for reconnaissance missions. Alternatively, platform 200 may bemore generic and include generic avionics equipment suitable for variousmissions, and/or one or more empty or partially empty equipment stationsin which additional avionics equipment may be disposed, depending onmission requirements. Accordingly, selected avionics equipment may bedisposed within the equipment station(s) during step 702.

Step 702 may also include providing at least one pair of mountingdevices 202, each mounting device 202 disposed on and axially alignedwith a respective one of opposing side portions 204 or 206 of framestructure 208 and configured to project outwardly from each respectiveopposing side portion 204 and 206 to align with and detachably secure tocorresponding airframe member 28 or 30 when frame structure 208 is in amounted position. In some embodiments, mounting devices 202 may bepre-disposed on frame structure 208. In other embodiments, mountingdevices 202 may be disposed on frame structure 208 during step 702. Inyet other embodiments, one or more mounting devices 202 may bepre-disposed on frame structure 208, and one or more additional mountingdevices 202 may be disposed on frame structure 208 during step 702.

In embodiments wherein one or more mounting devices 202 are disposed onframe structure 208 during step 702, mounting device(s) 202 may bedisposed on frame structure 208 with or without reference tocorresponding areas of airframe members 28 and 30 where mountingdevice(s) 202 are to be detachably secured. For example, in embodimentswherein complementary second mounting devices 278 are pre-attached toairframe members 28 and 30, each mounting device 202 may be disposed onframe structure 208 in alignment with and detachably secured by acorresponding second mounting device 278 disposed on airframe member 28or 30 when platform 200 is in the mounted position. Alternatively,mounting devices 202 may be disposed on frame structure 208 (before orduring step 702) without reference to positions of any pre-attachedsecond mounting devices 278. In such embodiments, second mountingdevices 278 may be attached to airframe members 28 and 30 to correspondwith positions of mounting devices 202 on frame structure 208 ofplatform 200. Additionally, some embodiments may include any number ofmounting devices 202 that are pre-attached and/or attached during step702.

A step 704 of method 700 may include detachably securing mountingdevices 202 to airframe members 28 and 30 by aligning each mountingdevice 202 with the corresponding second mounting device 278, to therebyremovably mount platform 200 within aircraft 12. Step 704 may includeproviding at least one pair of second mounting devices 278 disposed onairframe members 28 and 30 in positions corresponding to positions ofmounting devices 202 on frame structure 208, each second mounting device278 being configured to detachably secure a corresponding mountingdevice 202.

In some embodiments, second mounting devices 278 may be disposed onairframe members 28 and 30 prior to disposal of mounting devices 202 onframe structure 208. For example, aircraft 12 in which platform 200 isto be mounted may include second mounting devices 278 pre-disposed onairframe members 28 and 30 within forward interior bay 16, such as whereaircraft 12 may be manufactured to have second mounting devices 278within forward interior bay 16. In such embodiments, a user may not needto attach any second mounting devices 278 to airframe members 28 and 30.In alternative embodiments, as discussed above, one or more secondmounting devices 278 may be disposed on airframe members 28 and/or 30during step 704.

In embodiments wherein a number of second mounting devices 278 may bepre-disposed within forward interior bay 16, a user may neverthelesswish to attach one or more additional second mounting devices 278 tocorrespond with and support any additional mounting device(s) 202 thatmay be disposed on frame structure 208. Accordingly, a user may disposeone or more second mounting devices 278 on airframe members 28 and/or 30during step 704. For example, an access panel 44 located on the bottomor side(s) of forward interior bay 16 may be opened to provide access toforward interior bay 16, wherein any suitable number of second mountingdevices 278 may be disposed. Additionally, access panel 44 may provideaccess to forward interior bay 16 so that a user may make any necessarymeasurements, e.g., distance between opposing airframe members 28 and30, positions of second mounting devices 278 disposed on airframemembers 28 and 30, etc.

In embodiments wherein second mounting devices 278 include clampassemblies 276, mounting devices 202 may be secured to airframe members28 and 30 by pivoting a pivot clamp element 284 of each clamp assembly276 to a closed position to thereby removably mount frame structure 208within forward interior bay 16 of aircraft 12. Each pivot clamp element284 may then be locked into place to thereby secure mounting devices 202within clamp assemblies 276. In some embodiments, mounting devices 202may be secured within clamp assemblies 276 similar to securing a devicewithin a conventional vise; in other embodiments, mounting devices 202may be secured within clamp assembly 276 by locking pivot clamp element284 into place using a locking mechanism 294, described above withrespect to Example 1. Detachably securing each mounting device 202 tothe corresponding clamp assembly 276 thereby enables modularinstallation of selected avionics equipment into aircraft 12 to performa variety of equipment-dependent missions.

In embodiments wherein second mounting devices 278 include slots 274,mounting devices 202 may include pivot pins 212 configured to detachablysecure to airframe members 28 and 30 by extending into correspondingslots 274 in airframe members 28 and 30. Specifically, after aligningpivot pins 212 with corresponding slots 274, each pivot pin 212 may bepivoted into an extended position configured to extend into acorresponding slot 274 on airframe member 28 or 30 to thereby detachablysecure frame structure 208 to airframe members 28 and 30. Embodimentsmay include any number, combination, and configuration of slots 274,clamp assemblies 276, pivot pins 212, and/or mounting pins 210.

In some embodiments, step 704 may include inserting platform 200 intoforward interior bay 16 prior to detachably securing mounting devices202 of frame structure 208 to corresponding second mounting devices 278of airframe members 28 and 30. For example, platform 200 may be insertedinto forward interior bay 16 through an access panel 44 on the bottomand/or side(s) of aircraft 12 where forward interior bay 16 is located.Additionally, platform 200 may be hoisted into forward interior bay 16using a hoist knob 218 disposed on frame structure 208. Specifically,hoist knob 218 may be accessible through an access window 40 on an upperportion of forward interior bay 16, such as a gun mount upper access,and machinery or other suitable apparatus may attach to hoist knob 218to raise and/or lower platform 200 within forward interior bay 16.Additionally, platform 200 may be positioned within forward interior bay16 so that each mounting device 202 of frame structure 208 aligns withthe corresponding second mounting device 278 attached to correspondingairframe member 28 or 30 of forward interior bay 16.

In some cases, a user may wish to remove platform 200 from forwardinterior bay 16 of aircraft 12. Accordingly, an optional step 706 ofmethod 700 may include detaching mounting devices 202 of platform 200from airframe members 28 and 30 to thereby non-destructively releasablyremove platform 200 from forward interior bay 16. In embodiments whereinmounting devices 202 include clamp assemblies 276, mounting devices 202may be detached from clamp assemblies 276 by pivoting pivot clampelement 284 of each clamp assembly 276 to an open position 292. Inembodiments wherein mounting devices 202 include slots 274 and pivotpins 212, pivot pins 212 may be detached from slots 274 by pivoting eachpivot pin 212 to a recessed position stowed within a recessed area 213of a respective side portion 204 or 206 of frame structure 208.

In some embodiments, detachment of mounting devices 202 from secondmounting devices 278 may be accomplished by first providing support forplatform 200, such as by attaching hoist knob 218 to an externalhoisting apparatus, so that mounting devices 202 may be released withoutcausing platform 200 to fall. Platform 200 may then be removed fromforward interior bay 16, such as by using the external hoistingapparatus to lower platform 200 through access panel 44 located on abottom portion of forward interior bay 16.

A subsequent optional step 708 of method 700 may include interchangingplatform 200 with an alternate second platform 200′ configured tosupport an alternate set and/or configuration of selected avionicsequipment. Second platform 200′ may have substantially the sameconfiguration as platform 200, but include different avionics equipmentsupported thereon or therein. Accordingly, corresponding elements ofplatform 200′ are described using similar reference characters toplatform 200, but with the numbers primed. Step 708 may includeremovably mounting platform 200′ within forward interior bay 16 bydetachably securing mounting devices 202′ of second platform 200′ toairframe members 28 and 30 in substantially the same way as detachablysecuring mounting devices 202 of platform 200 during step 704. Removablemounting and interchanging of platform 200 and platform 200′ enables themodular installation of different avionics equipment into aircraft 12 toperform a variety of equipment-dependent missions.

In some embodiments, platform 200 may be reconfigured instead ofinterchanged with an alternate second platform 200′. Accordingly, anoptional step 708′ may be performed in lieu of step 708. Specifically,step 708′ of method 700 may include reconfiguring the avionics equipmentsupported by platform 200′ by rearranging, adding, and/or removing atleast one piece of avionics equipment supported by platform 200. Forexample, one or more avionics devices may be removed and replaced withone or more alternate avionics devices so that platform 200 may besuitable for a different equipment-dependent mission or set ofequipment-dependent missions.

A subsequent optional step 710 of method 700 may then includere-mounting platform 200 within forward interior bay 16 of aircraft 12in substantially the same way as during step 704, to thereby modularlyinstall different configurations, combinations, and/or sets of selectedavionics equipment within aircraft 12 using the same platform 200.

To reiterate, certain steps of method 700 may be performed in anysuitable order and/or combination. For example, in some embodiments,platform 200 may be reconfigured to support a different avionicsequipment setup during step 708′, remounted within aircraft 12 duringstep 710, unmounted from aircraft 12 in substantially the same way asduring step 706, and then interchanged with platform 200′ insubstantially the same way as during step 708. In other words, method700 may be performed in any manner suitable for modularly installingselected avionics equipment within aircraft 12 to perform a variety ofequipment-dependent missions.

Additional Features of Interchangeable Internal Avionics PlatformAssemblies

This section describes additional aspects and features ofinterchangeable internal avionics platform assemblies, presented withoutlimitation as a series of paragraphs, some or all of which may bealphanumerically designated for clarity and efficiency. Each of theseparagraphs can be combined with one or more other paragraphs, and/orwith disclosure from elsewhere in this application in any suitablemanner. Some of the paragraphs below expressly refer to and furtherlimit other paragraphs, providing without limitation examples of some ofthe suitable combinations.

Example 3

A0. An interchangeable modular avionics platform assembly, comprising aninterchangeable modular avionics platform including:

-   -   a frame structure having substantially parallel opposing side        portions spaced apart at a predetermined width so that the frame        structure fits between opposing airframe members within a        forward interior bay of a fuselage of an aircraft with each side        portion proximate a corresponding airframe member;    -   at least one pair of mounting pins, each mounting pin disposed        on and axially aligned with a respective one of the opposing        side portions of the frame structure and configured to project        outwardly from each respective opposing side portion to align        with and detachably secure to the corresponding airframe member        when the frame structure is in a mounted position; and    -   a connector assembly disposed on the frame structure and having        a plurality of connectors, including an alternating current        connector configured to connect to a 115-volt alternating        current source, a direct current connector configured to connect        to a 28-volt direct current source, and a data bus connector        configured to connect to a data bus of the aircraft;    -   wherein the modular avionics platform is mountable within and        non-destructively releasably removable from the forward interior        bay of the fuselage as to be interchangeable with a number of        alternate modular avionics platforms, with each modular avionics        platform being configured to support one or more of avionics        equipment having different dimensions, and to thereby enable        modular installation of selected avionics equipment into the        aircraft to perform a variety of equipment-dependent missions.

A1. The interchangeable modular avionics platform assembly of paragraphA0, further comprising a clamp assembly configured to be attached to theopposing airframe member corresponding to each position of the mountingpins on the frame structure, each clamp assembly having a fixed clampelement configured to be fixedly attached to the airframe member, and apivot clamp element configured to pivot between an open position inwhich the pivot clamp element is spaced apart from the fixed clampelement, and a closed position in which the pivot clamp element isproximate to and secured relative to the fixed clamp element to clampthe corresponding mounting pin to the corresponding airframe member andthereby enable removable mounting of the frame structure to the airframemembers

A2. The interchangeable modular avionics platform assembly of paragraphA0, wherein the at least one pair of mounting pins comprises a secondpair of mounting pins spaced apart from the one pair of mounting pins,each pair of mounting pins configured to provide support for theplatform on the airframe members.

A3. The interchangeable modular avionics platform assembly of paragraphA0, wherein the modular avionics platform further comprises a firstequipment rack having first equipment station and configured to supportand enable detachable securement of selected avionics equipment thereon,a second equipment rack having a second and third equipment stations,and an environmental cooling system, the environmental cooling systemincluding a compressor and a cooling fan mounted in the third equipmentstation, and a length of flexible cooling tubing that is in fluidcommunication with the cooling fan and extends to the second equipmentstation to thereby supply cooling air to the second equipment station.

A4. The interchangeable modular avionics platform assembly of paragraphA3, wherein the environmental cooling system further comprises flexibleexhaust tubing configured to communicate the cooling air for heatremoval from the second equipment station to louvers in the forwardinterior bay of the fuselage for venting therethrough.

A5. The interchangeable modular avionics platform assembly of paragraphA0, wherein the modular avionics platform further comprises at least oneequipment rack having a plurality of equipment stations configured tosupport and enable detachable securement of selected avionics equipmentthereon.

A6. The interchangeable modular avionics platform assembly of paragraphA5, wherein the modular avionics platform further comprises a data linksystem disposed on the equipment rack and configured to sense andreceive data communicated between aircraft communication nodes, toenable at least one airborne aircraft to control firing of otherairborne aircraft weaponry at a designated target by communicating usingthe data link system.

A7. The interchangeable modular avionics platform assembly of paragraphA5, wherein the modular avionics platform further comprises an infraredsearch-and-track sensor system disposed on the equipment rack andconfigured to enable tracking of other airborne aircraft.

A8. The interchangeable modular avionics platform assembly of paragraphA5, wherein the modular avionics platform further comprises aninternet-protocol-based mesh-network radio terminal disposed on theequipment rack and configured to enable data communication betweenmultiple airborne aircraft including the aircraft in which the modularavionics platform is mounted.

A9. The interchangeable modular avionics platform assembly of paragraphA0, wherein the modular avionics platform further comprises a pair ofpivot pins, each pivot disposed on and axially aligned with a respectiveone of the opposing side portions of the frame structure and positionedto align with a corresponding slot on the corresponding airframe memberwhen the frame structure is in a mounted position, and configured tohave a stowed position recessed within the respective side portion ofthe frame structure, and an extended position configured to extend intothe corresponding slot on the opposing airframe member to therebydetachably secure the frame structure to the airframe members.

A10. The interchangeable modular avionics platform assembly of paragraphA0, wherein the frame structure includes first and second equipmentracks with the first equipment rack disposed above the second equipmentrack.

B0. An aircraft comprising:

-   -   a forward interior bay of a fuselage of the aircraft having        laterally opposing airframe members and configured for removable        mounting of a gun therein;    -   an interchangeable modular avionics platform removably mounted        to the airframe members within the forward interior bay, wherein        the platform includes a substantially rectangular frame        structure having opposing side portions proximate to the        airframe members, and wherein the frame structure includes a        plurality of outwardly projecting mounting pins disposed on and        axially aligned with the side portions, including a first pair        of mounting pins and a second pair of mounting pins spaced apart        from the first pair of mounting pins, each mounting pin        positioned on the frame structure to align with and detachably        secure to a corresponding clamp assembly disposed on the        airframe members; and    -   a plurality of clamp assemblies disposed on the airframe members        in positions corresponding to positions of the mounting pins on        the frame structure, including a first pair of clamp assemblies        corresponding to the first pair of mounting pins and a second        pair of clamp assemblies corresponding to the second pair of        mounting pins, each clamp assembly configured to detachably        secure a corresponding mounting pin and having a fixed clamp        element fixedly attached to a respective airframe member, and a        pivot clamp element configured to pivot between an open position        in which the corresponding mounting pin is not clamped, and a        closed position in which the corresponding mounting pin is        clamped into place relative to the clamp assembly;    -   the modular avionics platform being configured to be mountable        within and non-destructively releasably removable from the        forward interior bay of the fuselage by the plurality of clamp        assemblies as to be interchangeable with a number of alternate        modular avionics platforms, with each modular avionics platform        being configured to support one or more of avionics equipment        having different dimensions, and to thereby enable modular        installation of selected avionics equipment into the aircraft to        perform a variety of equipment-dependent missions.

B1. The aircraft of paragraph B0, wherein the modular avionics platformfurther comprises a connector assembly disposed on the frame structureand having a plurality of connectors, including an alternating currentconnector configured to connect to a 115-volt alternating currentsource, a direct current connector configured to connect to a 28-voltdirect current source, and a data bus connector configured to connect toa data bus of the aircraft.

B2. The aircraft of paragraph B0, wherein the modular avionics platformfurther comprises at least one equipment rack supported on the framestructure and having a plurality of equipment stations, including afirst equipment station and a second equipment station, each equipmentstation being configured to support and enable detachable securement ofselected avionics equipment therein.

B3. The aircraft of paragraph B2, wherein the modular avionics platformfurther comprises a third equipment station supported on the framestructure and an environmental cooling system including a compressor andcooling fan supported in the third equipment station, and a length offlexible cooling tubing in fluid communication with the cooling fan andconfigured to extend to the second equipment station to thereby supplycooling air to at least one electrical component disposed within thesecond equipment station.

B4. The aircraft of paragraph B3, wherein the environmental coolingsystem further comprises flexible exhaust tubing configured tocommunicate the cooling air for heat removal from the second equipmentstation to louvers in the forward interior bay of the fuselage forventing therethrough.

B5. The aircraft of paragraph B2, wherein the modular avionics platformfurther comprises a data link system disposed on the equipment rack andconfigured to sense and receive data communicated between aircraftcommunication nodes, and to enable at least one airborne aircraft tocontrol firing of other airborne aircraft weaponry at a designatedtarget by communicating using the data link system.

B6. The aircraft of paragraph B2, wherein the modular avionics platformfurther comprises an infrared search-and-track sensor system disposed onthe equipment rack and configured to enable tracking of other airborneaircraft.

B7. The aircraft of paragraph B2, wherein the modular avionics platformfurther comprises an internet-protocol-based mesh-network radio terminaldisposed on the equipment rack and configured to enable datacommunication between multiple airborne aircraft including the aircraftin which the modular avionics platform is mounted.

C0. A method for removably mounting an interchangeable modular avionicsplatform within a forward interior bay of a fuselage of an aircraft,comprising:

-   -   providing an interchangeable modular avionics platform        configured to support selected avionics equipment having        different dimensions, and including a frame structure having        substantially parallel opposing side portions spaced apart at a        predetermined width so that the frame structure fits between        opposing airframe members within the forward interior bay of the        aircraft with each side portion proximate a corresponding        airframe member;    -   providing at least one pair of first mounting devices, each        first mounting device disposed on and axially aligned with a        respective one of the opposing side portions of the frame        structure and configured to project outwardly from each        respective opposing side portion to align with and detachably        secure to the corresponding airframe member when the frame        structure is in a mounted position;    -   providing at least one pair of complementary second mounting        devices disposed on the airframe members in positions        corresponding to positions of the first mounting devices on the        frame structure, each second mounting device configured to        detachably secure a corresponding first mounting device and        having a fixed clamp element fixedly attached to a respective        airframe member, and a pivot clamp element configured to pivot        between an open position in which the corresponding first        mounting device is not clamped, and a closed position in which        the corresponding first mounting device is clamped into place        relative to the second mounting device;    -   detachably securing the first mounting devices of the frame        structure to the airframe members by aligning each first        mounting device with a corresponding second mounting device and        pivoting the pivot clamp element of each second mounting device        to the closed position to thereby removably mount the frame        structure within the forward interior bay of the fuselage as to        be interchangeable with a number of alternate modular avionics        platforms, thus enabling modular installation of selected        avionics equipment into the aircraft to perform a variety of        equipment-dependent missions.

C1. The method of paragraph C0, further comprising non-destructivelyreleasing the frame structure from the airframe members within theforward interior bay of the fuselage by pivoting the pivot clamp elementof each second mounting device to the open position to unclamp thecorresponding first mounting device and thereby enable removal of themodular avionics platform from the aircraft.

C2. The method of paragraph C1, further comprising providing andremovably mounting an alternate modular avionics platform within theforward interior bay of the fuselage, wherein the alternate modularavionics platform is configured to support alternate avionics equipment,to thereby modularly install different avionics equipment within theaircraft.

C3. The method of paragraph C1, further comprising reconfiguring theavionics equipment supported by the modular avionics platform by atleast one of rearranging, adding, and removing at least one piece ofavionics equipment supported by the modular avionics platform.

C4. The method of paragraph C3, further comprising re-mounting themodular avionics platform within the forward interior bay of thefuselage to thereby modularly install different configurations ofselected avionics equipment within the aircraft.

Advantages, Features, Benefits

The different embodiments of the interchangeable internal modularavionics platform assembly described herein provide several benefits.For example, the illustrative embodiments of modular avionics platformassemblies described herein allow for selected avionics equipment to beremovably mounted within an interior bay of any aircraft, therebyincreasing external stores capability of the aircraft. Additionally, andamong other benefits, illustrative embodiments of the modular avionicsplatform assembly described herein may allow for the easy installation,removal, and interchanging of various modular avionics platforms withinthe aircraft, thereby enabling modular installation of avionicsequipment into the aircraft to perform a variety of equipment-dependentmissions. Thus, the illustrative embodiments described herein areparticularly useful for situations requiring a high degree ofmodularity. However, not all embodiments described herein provide thesame benefits or the same amount of benefit.

Conclusion

The disclosure set forth above may encompass multiple distinctinventions with independent utility. Although each of these inventionshas been disclosed in its preferred form(s), the specific embodimentsthereof as disclosed and illustrated herein are not to be considered ina limiting sense, because numerous variations are possible. Each exampledefines an embodiment disclosed in the foregoing disclosure, but any oneexample does not necessarily encompass all features or combinations thatmay be eventually claimed. Where the description recites “a” or “afirst” element or the equivalent thereof, such description includes oneor more such elements, neither requiring nor excluding two or more suchelements. Further, ordinal indicators, such as first, second or third,for identified elements are used to distinguish between the elements,and do not indicate a required or limited number of such elements, anddo not indicate a particular position or order of such elements unlessotherwise specifically stated.

To the extent that section headings are used within this disclosure,such headings are for organizational purposes only, and do notconstitute a characterization of any claimed invention. The subjectmatter of the invention(s) includes all novel and nonobviouscombinations and subcombinations of the various elements, features,functions, and/or properties disclosed herein. The following claimsparticularly point out certain combinations and subcombinations.Invention(s) embodied in other combinations and subcombinations offeatures, functions, elements, and/or properties may be claimed inapplications claiming priority from this or a related application. Suchclaims, whether directed to a different invention or to the sameinvention, and whether broader, narrower, equal, or different in scopeto the original claims, also are regarded as included within the subjectmatter of the invention(s) of the present disclosure.

I claim:
 1. An interchangeable modular avionics platform assembly,comprising an interchangeable modular avionics platform including: aframe structure having substantially parallel opposing side portionsspaced apart at a predetermined width so that the frame structure fitsbetween opposing airframe members within a forward interior bay of afuselage of an aircraft with each side portion proximate a correspondingairframe member; at least one pair of mounting pins, each mounting pindisposed on and axially aligned with a respective one of the opposingside portions of the frame structure and configured to project outwardlyfrom each respective opposing side portion to align with and detachablysecure to the corresponding airframe member when the frame structure isin a mounted position; and a connector assembly disposed on the framestructure and having a plurality of connectors, including an alternatingcurrent connector configured to connect to a 115-volt alternatingcurrent source, a direct current connector configured to connect to a28-volt direct current source, and a data bus connector configured toconnect to a data bus of the aircraft; wherein the modular avionicsplatform is mountable within and non-destructively releasably removablefrom the forward interior bay of the fuselage as to be interchangeablewith a number of alternate modular avionics platforms, with each modularavionics platform being configured to support one or more of avionicsequipment having different dimensions, and to thereby enable modularinstallation of selected avionics equipment into the aircraft to performa variety of equipment-dependent missions.
 2. The interchangeablemodular avionics platform assembly of claim 1, further comprising aclamp assembly configured to be attached to the opposing airframe membercorresponding to each position of the mounting pins on the framestructure, each clamp assembly having a fixed clamp element configuredto be fixedly attached to the airframe member, and a pivot clamp elementconfigured to pivot between an open position in which the pivot clampelement is spaced apart from the fixed clamp element, and a closedposition in which the pivot clamp element is proximate to and securedrelative to the fixed clamp element to clamp the corresponding mountingpin to the corresponding airframe member and thereby enable removablemounting of the frame structure to the airframe members
 3. Theinterchangeable modular avionics platform assembly of claim 1, whereinthe at least one pair of mounting pins comprises a second pair ofmounting pins spaced apart from the one pair of mounting pins, each pairof mounting pins configured to provide support for the platform on theairframe members.
 4. The interchangeable modular avionics platformassembly of claim 1, wherein the modular avionics platform furthercomprises a first equipment rack having first equipment station andconfigured to support and enable detachable securement of selectedavionics equipment thereon, a second equipment rack having a second andthird equipment stations, and an environmental cooling system, theenvironmental cooling system including a compressor and a cooling fanmounted in the third equipment station, and a length of flexible coolingtubing that is in fluid communication with the cooling fan and extendsto the second equipment station to thereby supply cooling air to thesecond equipment station.
 5. The interchangeable modular avionicsplatform assembly of claim 4, wherein the environmental cooling systemfurther comprises flexible exhaust tubing configured to communicate thecooling air for heat removal from the second equipment station tolouvers in the forward interior bay of the fuselage for ventingtherethrough.
 6. The interchangeable modular avionics platform assemblyof claim 1, wherein the modular avionics platform further comprises atleast one equipment rack having a plurality of equipment stationsconfigured to support and enable detachable securement of selectedavionics equipment thereon.
 7. The interchangeable modular avionicsplatform assembly of claim 6, wherein the modular avionics platformfurther comprises a data link system disposed on the equipment rack andconfigured to sense and receive data communicated between aircraftcommunication nodes, to enable at least one airborne aircraft to controlfiring of other airborne aircraft weaponry at a designated target bycommunicating using the data link system.
 8. The interchangeable modularavionics platform assembly of claim 6, wherein the modular avionicsplatform further comprises an infrared search-and-track sensor systemdisposed on the equipment rack and configured to enable tracking ofother airborne aircraft.
 9. The interchangeable modular avionicsplatform assembly of claim 6, wherein the modular avionics platformfurther comprises an internet-protocol-based mesh-network radio terminaldisposed on the equipment rack and configured to enable datacommunication between multiple airborne aircraft including the aircraftin which the modular avionics platform is mounted.
 10. Theinterchangeable modular avionics platform assembly of claim 1, whereinthe modular avionics platform further comprises a pair of pivot pins,each pivot disposed on and axially aligned with a respective one of theopposing side portions of the frame structure and positioned to alignwith a corresponding slot on the corresponding airframe member when theframe structure is in a mounted position, and configured to have astowed position recessed within the respective side portion of the framestructure, and an extended position configured to extend into thecorresponding slot on the opposing airframe member to thereby detachablysecure the frame structure to the airframe members.
 11. Theinterchangeable modular avionics platform assembly of claim 1, whereinthe frame structure includes first and second equipment racks with thefirst equipment rack disposed above the second equipment rack.
 12. Anaircraft comprising: a forward interior bay of a fuselage of theaircraft having laterally opposing airframe members and configured forremovable mounting of a gun therein; an interchangeable modular avionicsplatform removably mounted to the airframe members within the forwardinterior bay, wherein the platform includes a substantially rectangularframe structure having opposing side portions proximate to the airframemembers, and wherein the frame structure includes a plurality ofoutwardly projecting mounting pins disposed on and axially aligned withthe side portions, including a first pair of mounting pins and a secondpair of mounting pins spaced apart from the first pair of mounting pins,each mounting pin positioned on the frame structure to align with anddetachably secure to a corresponding clamp assembly disposed on theairframe members; and a plurality of clamp assemblies disposed on theairframe members in positions corresponding to positions of the mountingpins on the frame structure, including a first pair of clamp assembliescorresponding to the first pair of mounting pins and a second pair ofclamp assemblies corresponding to the second pair of mounting pins, eachclamp assembly configured to detachably secure a corresponding mountingpin and having a fixed clamp element fixedly attached to a respectiveairframe member, and a pivot clamp element configured to pivot betweenan open position in which the corresponding mounting pin is not clamped,and a closed position in which the corresponding mounting pin is clampedinto place relative to the clamp assembly; the modular avionics platformbeing configured to be mountable within and non-destructively releasablyremovable from the forward interior bay of the fuselage by the pluralityof clamp assemblies as to be interchangeable with a number of alternatemodular avionics platforms, with each modular avionics platform beingconfigured to support one or more of avionics equipment having differentdimensions, and to thereby enable modular installation of selectedavionics equipment into the aircraft to perform a variety ofequipment-dependent missions.
 13. The aircraft of claim 12, wherein themodular avionics platform further comprises a connector assemblydisposed on the frame structure and having a plurality of connectors,including an alternating current connector configured to connect to a115-volt alternating current source, a direct current connectorconfigured to connect to a 28-volt direct current source, and a data busconnector configured to connect to a data bus of the aircraft.
 14. Theaircraft of claim 12, wherein the modular avionics platform furthercomprises at least one equipment rack supported on the frame structureand having a plurality of equipment stations, including a firstequipment station and a second equipment station, each equipment stationbeing configured to support and enable detachable securement of selectedavionics equipment therein.
 15. The aircraft of claim 14, wherein themodular avionics platform further comprises a third equipment stationsupported on the frame structure and an environmental cooling systemincluding a compressor and cooling fan supported in the third equipmentstation, and a length of flexible cooling tubing in fluid communicationwith the cooling fan and configured to extend to the second equipmentstation to thereby supply cooling air to at least one electricalcomponent disposed within the second equipment station.
 16. The aircraftof claim 15, wherein the environmental cooling system further comprisesflexible exhaust tubing configured to communicate the cooling air forheat removal from the second equipment station to louvers in the forwardinterior bay of the fuselage for venting therethrough.
 17. The aircraftof claim 14, wherein the modular avionics platform further comprises adata link system disposed on the equipment rack and configured to senseand receive data communicated between aircraft communication nodes, andto enable at least one airborne aircraft to control firing of otherairborne aircraft weaponry at a designated target by communicating usingthe data link system.
 18. The aircraft of claim 14, wherein the modularavionics platform further comprises an infrared search-and-track sensorsystem disposed on the equipment rack and configured to enable trackingof other airborne aircraft.
 19. The aircraft of claim 14, wherein themodular avionics platform further comprises an internet-protocol-basedmesh-network radio terminal disposed on the equipment rack andconfigured to enable data communication between multiple airborneaircraft including the aircraft in which the modular avionics platformis mounted.